Turbine engine airfoil
An airfoil is provided that includes a first end, a second end, a leading edge, a trailing edge, a pressure side and a suction side. The leading edge and the trailing edge are joined by the pressure side and the suction side to provide an exterior airfoil surface extending in a spanwise direction from the first end of the airfoil to the second end of the airfoil. The exterior airfoil surface is formed in conformance with a plurality of cross-section profiles of the airfoil described by a set of Cartesian coordinates set forth in Table 1. The Cartesian coordinates are provided by an axial coordinate scaled by a local axial chord, a circumferential coordinate scaled by the local axial chord, and a span location. The local axial chord corresponds to a width of the airfoil between the leading edge and the trailing edge at the span location.
1 . An apparatus for a turbine engine, comprising:
an airfoil including a first end, a second end, a leading edge, a trailing edge, a pressure side and a suction side;
the leading edge and the trailing edge joined by the pressure side and the suction side to provide an exterior airfoil surface extending in a spanwise direction from the first end of the airfoil to the second end of the airfoil;
the exterior airfoil surface formed in conformance with a plurality of cross-section profiles of the airfoil described by a set of Cartesian coordinates which includes each Cartesian coordinate set forth in Table 1;
the Cartesian coordinates provided by an axial coordinate scaled by a local axial chord, a circumferential coordinate scaled by the local axial chord, and a span location; and
the local axial chord corresponding to a width of the airfoil between the leading edge and the trailing edge at the span location.
2 . The apparatus of claim 1 , wherein the span location corresponds to a distance from a rotational axis of the turbine engine.
3 . The apparatus of claim 1 , further comprising:
an inner platform connected to the airfoil at the first end of the airfoil; and
an outer platform connected to the airfoil at the second end of the airfoil.
4 . The apparatus of claim 1 , wherein the apparatus comprises a turbine vane.
5 . The apparatus of claim 4 , wherein the turbine vane is a low pressure turbine vane.
6 . The apparatus of claim 1 , further comprising a coating applied over the exterior airfoil surface.
7 . The apparatus of claim 1 , wherein the airfoil is configured without an internal cooling passage.
8 . The apparatus of claim 1 , wherein the airfoil is one of thirty-six airfoils arranged circumferentially about an axis in an annular array.
9 . A stator vane structure for a turbine engine, comprising:
a first platform;
a second platform; and
a plurality of stator vanes arranged circumferentially about an axis in an array, each of the plurality of stator vanes comprising an airfoil;
the airfoil including a leading edge, a trailing edge, a pressure side and a suction side;
the leading edge and the trailing edge joined by the pressure side and the suction side to provide an exterior airfoil surface extending in a spanwise direction from the first platform to the second platform;
the exterior airfoil surface formed in conformance with a plurality of cross-section profiles of the airfoil defined by a set of Cartesian coordinates which includes each Cartesian coordinate set forth in Table 1, wherein the set of Cartesian coordinates have a tolerance of +/−0.050 inches;
the Cartesian coordinates provided by an axial coordinate scaled by a local axial chord, a circumferential coordinate scaled by the local axial chord, and a span location; and
the local axial chord corresponding to a width of the airfoil between the leading edge and the trailing edge at the span location.
10 . The stator vane structure of claim 9 , wherein the span location corresponds to a distance from the axis.
11 . The stator vane structure of claim 9 , wherein the plurality of stator vanes are turbine vanes.
12 . The stator vane structure of claim 9 , wherein the exterior airfoil surface is partially or completely covered by a coating.
13 . The stator vane structure of claim 9 , wherein the plurality of stator vanes consist of thirty-six stator vanes.
14 . A turbine engine, comprising:
a flowpath, a compressor section, a combustor section and a turbine section;
the flowpath extending through the compressor section, the combustor section and the turbine section from an inlet into the flowpath to an exhaust from the flowpath;
the turbine section including a plurality of turbine vanes arranged circumferentially about an axis in an array, each of the plurality of turbine vanes comprising an airfoil located in the flowpath;
the airfoil including a first end, a second end, a leading edge, a trailing edge, a pressure side and a suction side;
the leading edge and the trailing edge joined by the pressure side and the suction side to provide an exterior airfoil surface extending in a spanwise direction from the first end of the airfoil to the second end of the airfoil;
the exterior airfoil surface formed in conformance with a plurality of cross-section profiles of the airfoil defined by a set of Cartesian coordinates which includes each Cartesian coordinate set forth in Table 1;
the Cartesian coordinates provided by an axial coordinate scaled by a local axial chord, a circumferential coordinate scaled by the local axial chord, and a span location; and
the local axial chord corresponding to a width of the airfoil between the leading edge and the trailing edge at the span location.
15 . The turbine engine of claim 14 , wherein the turbine section includes a high pressure turbine section and a low pressure turbine section, and the low pressure turbine section includes the plurality of turbine vanes.
16 . The turbine engine of claim 15 , wherein the plurality of turbine vanes are part of a first stage of the low pressure turbine section.
17 . The turbine engine of claim 15 , further comprising a coating applied over the exterior airfoil surface.